Abstract
A laboratory procedure for making a lightweight (128 kg/m3 (8 lb/ft3) Fibrous Refractory Composite Insulation (FRCI) was scaled up to a pilot-plant process at Lockheed Missiles & Space Co., Inc., (LMSC) in 1979. Thermal performance of this material was unacceptable for the intended application on the Space Shuttle Orbiter. However, the mechanical properties were acceptable. An FRCl material at 136 kg/m3 (8.5 lb/ft3) with acceptable thermal performance was developed by varying processing and compositional factors.
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